Measurement of static pressure in transonic turbines is made difficult because of the need to use probes with substantial support stems in the measurement plane, enabling them to traverse in the confined axial spaces between blade rows. Problems arise because of shock interactions with the probes and the close proximity of shock-reflecting surfaces. Tests show that the calibration can depend on the proportion of probe support immersed in the transonic flow. The wind tunnel gives only partial representation of the turbine transonic flow field, but by using turbine measured and computed static pressures the most representative calibration is selected.

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